Aeroplane



J. D. BENSON.

AEROPLANE.

APPLICATION FILED NOV. 5,1918.

Patented Apr. 13, 1920.

2 SHE S--SHEET 1.

J. D. BENSON.'

AEBOPLANE. APPLFcATloN HlLED Nov. 5, 191s.

Patented Apr. 13, 1920.

2 SHEETS-SHEET 2.

lu/wanton UNITED STATES PATENT OFFICE.

J'ESSIE D. BENSON, OF GRAND RAPIDS, MICHIGAN.

AEROPLANE.

Application filed November 5, 1918.

To all 'whom t may concern:

Be it known that I, .Inseln D. DENsoN, a citizen of the United States, residing at Grand Rapids, in the county of Kent, State of Michigan, have invented certain new and useful Improvements in Aeroplanes; and I do hereby declare the following to be a full, clear, and exact description of the invention, such as will enable others skilled in the art to which it appertains to make and use the same.

This invention relates to new and useful improvements in aeronautics and particularly to aeroplanes.

One object of the present invention is to provide a novel and improved aeroplane which includes an adjustable air chamber operable by the aviator.

A further object is to provide novel and improved means for regulating the adjustment of the air chamber whereby a greater or lesser amount of air can be permitted to enter the chamber for the purpose of checking a precipitate downward flight.

Other objects and advantages will be apparent from the following description when taken in connection with the accompanying drawings.

In the drawings:

Figure l is a top plan viewrof an aeroplane made in accordance with my invention, the ends of the sustaining planes being broken away.

Fig. 2 is a fragmentary top plan view partly broken away.

Fig. 3 is a vertical longitudinal sectional view taken on the line 3 3 of Fig. l.

Fig. 4 is a vertical transverse sectional view taken on the line 4-4 of Fig. 3.

Fig. 5 is a perspective view of the tail of the aeroplane showing the same expanded when filled with air.

Referring particularly to the accompanying drawings, 10 represents the body or fuselage of the aeroplane, the rear end of which is widened at 11 to a certain degree and formed into a chamber 11.

A transverse shaft 28 is mounted in the forward portion of the fuselage and on the intermediate portion of this shaft there are mounted the two oppositely extending radial arms 29, one of which is pivotally connected to a foot lever 30, while the other is pivotally connected to the forward end of a Specification of Letters Patent.

Patented Apr. 13, 1920.

Serial No. 261,260.

forwardly and rearwardly sliding rod 31. Pivotally connected to the rear end of the rod 3l, is the forward end of a second rod 32, the rear end of this second rod being slidably supported in an opening 33 in the rear central portion of the tail l1. Two oppositely extending arms 34 and 35 are also carried by the shaft 28, the former being connected to the upper of the arms 29 to form the crank 36, while the latter is connected to the lower arm 29 to form the crank 37. To this crank 3l is connected to beforementioned lever 30, while a second foot lever 38 is connected to the crank 3G. Thus when the lever 30 is pushed forwardly the rods 3l and 32 will be moved forwardly, while when the lever 38 is pushed forwardly the rods will be moved rearwardly. One of the levers will be up and the other down, at all times, as will be seen from the drawings.

Mounted on a transverse shaft 39 are the upwardly extending arms 40, both of which are pivotally connected to the bottom of a platform member 4l, disposed thereabove. This platform is carried by the forward end of a board or member 42 which extends from the rear edges of the sustaining planes to the rear end of the tail 11, and thereabove. Connecting this board with the sides and rear of the tail, is a water and air proof fabric 43. Mounted in the fuselage is an operating lever 44 which is connected to the shaft 39 by means of the arm 45 and the link 46. By means of this lever, and its connections with the member 4l, the member 42 may be adjusted up and down whereby the forward or mouth end of the air chamber, formed by the member 42 and the fabric, may be opened and closed to the desired degree, thus permitting 0r preventing the entrance of air to the chamber.

The propeller 47 is driven in the usual manner, the engine and connections to the propeller not being shown.

Extending upwardly from the rear portion of the upper face of the member 42 is a fin 48.

Should the aeroplane make a nose dive, the aviator can check the too rapid descent of the machine by pressing on the pedal lever 38. By operating one or the other of the pedals 30 or 38, and the lever 44, the aviator can control the opening and closing of the mouth of the air chamber of the tail to regulate the speed at which he will drop through the air.

What is claimed is:

l. An aeroplane including a fuselage having the tail portion formed with a braking member subject to change in its cross sectional area by air pressure, and means for controlling the entrance of air pressure to said braking member.

2. An aeroplane including a fuselage having a braking member in the tail thereof, one end of the member being open to receive air pressure to change the cross sectional area thereof, and means for controlling the passage of air pressure through said opening.

3.An aeroplane includino' a fuselage, a collapsible air receiving chamber in the tail of the fuselage, the forward end of the chamber being open to receive air during flight, and means for controlling the said open end to regulate the amount of air entering the chamber.

4C. An aeroplane having a collapsible tail member formed with a forward open end for receiving air during flight, a rocking member forming a part of the collapsible tail member, and a means operable by the aviator for controlling the movements of the rocking member tov regulate the amount of air entering the tail member.

5. An aeroplane including a collapsible air receiving tail member, the forward end of the tail member adapted to be opened to receive air during flight, a rocking member for opening and closing said end, and a slidable fulcrum for the rocking member.

6. An aeroplane including a collapsible air receiving and flight checking tail member, a rocking member forming the top of the tail member, a slidable fulcrum for the rocking member, and means for moving the said slidable fulcrum to regulate the amount of air entering the tail member.

In testimony whereof, l ailix my signature, in the presence of two witnesses.

JESSIE l). BENSON.

Witnesses ROBERT C. BowMAN, HERMAN HILLIARD. 

